National Advisory Committee for Aeronautics (NACA) - 14 Matching Results

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The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Description: From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date: September 1950
Creator: Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis for Control Application of Dynamic Characteristics of Turbojet Engine With Tail-Pipe Burning

Description: "The first basic problem that must be solved before control synthesis can proceed is that of determining the dynamic characteristics of the engine. Accordingly, an analysis of the dynamic behavior of the turbojet engine with tail-pipe burning was made at the NACA Lewis laboratory and is presented herein" (p. 1).
Date: September 1950
Creator: Feder, Melvin S. & Hood, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of effect of variations in primary variables on time constant and turbine-inlet-temperature overshoot of turbojet engine

Description: From Introduction: "The design of turbojet-engine control systems is intimately related to the dynamic characteristics of the engine and has advanced to the stage where theoretically correct control constants can be determined for fixed dynamic properties (references 1 and 2). The use of the thermodynamic equations presupposes that the engine processes are quansi-static. Such an assumption is shown to be valid for a turbojet engine in references 3 and 4.
Date: September 1950
Creator: Heidmann, Marcus F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The development and performance of two small tunnels capable of intermittent operation at Mach numbers between 0.4 and 4.0

Description: Report presenting the design, development, and performance of equipment suitable for use by educational institutions for student training and basic compressible-flow research. Supersonic nozzles designed for a range of Mach numbers were tested in the blowdown tunnel and produced average Mach numbers close to the design values.
Date: September 1950
Creator: Lindsey, Walter F. & Chew, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effectiveness of molybdenum disulfide as a fretting-corrosion inhibitor

Description: Report presenting an investigation of the effectiveness of molybdenum disulfide as a fretting-corrosion inhibitor. Six methods of applying MoS2 to steel specimens was evaluated by noting the number of cycles of vibration required to produce the first evidence of fretting corrosion and by observing the nature of its occurrence. Experiments were conducted with steel balls vibrating in contact with glass flats whereby the action could be microscopically observed.
Date: September 1950
Creator: Godfrey, Douglas & Bisson, Edmond E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Stiffened Circular Cylinders Subjected to Combined Torsion and Compression

Description: "Five stiffened circular cylinders were tested to failure under various combinations of torsion and compression. The results of the tests are presented in the form of plots of stringer stress against cylinder load and an interaction curve for the strength of stringers that fail by local crippling. A method is given for calculating stiffener stresses in cylinders subjected to combined loads, and a comparison between calculated and experimental stringer stresses is made" (p. 1).
Date: September 1950
Creator: Peterson, James P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Two-Step Nozzle in the Langley 11-Inch Hypersonic Tunnel

Description: Report presenting flow surveys made in a nozzle investigated in the 11-inch hypersonic tunnel. The nozzle was designed for a Mach number of 6.98 and was tested using a two 2-dimensional steps to gradually expand the air in the horizontal and vertical planes. The flow in the test was not sufficiently uniform for quantitative wind-tunnel test purposes.
Date: September 1950
Creator: McLellan, Charles H.; Williams, Thomas W. & Bertram, Mitchel H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of frequency-response characteristics of engine speed for a typical turbine-propeller engine

Description: Report presenting the experimental frequency-response characteristics of engine speed for a typical turbine-propeller engine. The data were obtained by subjecting the engine to sinusoidal variation of fuel flow and propeller-blade-angle inputs. A comparison of the analytical and experimental results is provided.
Date: September 1950
Creator: Taylor, Burt L., III & Oppenheimer, Frank L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for determining optimum division of power between jet and propeller for maximum thrust power of a turbine-propeller engine

Description: Report presenting charts by which the jet pressure ratio that gives optimum division of power between propeller and jet for maximum total thrust power may be determined for any turbine-propeller engine with or without intercooling, reheat, regeneration, or any combination of the three modifications. The method of obtaining optimum power division is compared for two sets of conditions with two other methods that have been widely used.
Date: September 1950
Creator: Trout, Arthur M. & Hall, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method for Determining Pressure Drop of Air Flowing Through Constant-Area Passages for Arbitrary Heat-Input Distributions

Description: Report presenting a method for convenient determination of the pressure drop sustained by air flowing at high subsonic speeds in a constant-area passage under the simultaneous influence of friction and heat addition. Air-pressure-drop working charts based on the method are presented.
Date: September 1950
Creator: Pinkel, Benjamin; Noyes, Robert N. & Valerino, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Sonic-Flow-Orifice Temperature Probe for High-Gas-Temperature Measurements

Description: Note presenting a temperature-measuring device using sonic-flow orifices and a comparison with existing temperature-measuring instruments. The device was compared with a standard shielded thermocouple in the temperature range from 710 to 1160 degrees R and excellent agreement was obtained. Limitations and sources of errors of the device are discussed.
Date: September 1950
Creator: Blackshear, Perry L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A survey of the flow at the plane of the propeller of a twin-engine airplane

Description: Report presenting a survey of the air flow at the plane of the propeller of a full-scale twin-engine airplane to provide data for use in the calculation of oscillating aerodynamic loadings on propellers. The investigation was conducted through a range of angles of attack for two nacelle inlet mass-flow ratios. Results regarding the upwash characteristics and effect of the flow field on the oscillating aerodynamic loading on a propeller are provided.
Date: September 1950
Creator: Roberts, John C. & Yaggy, Paul F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turning-Angle Design Rules for Constant-Thickness Circular-Arc Inlet Guide Vanes in Axial Annular Flow

Description: Note presenting a survey of data from investigations of axial-flow-compressor inlet guide vanes with circular-arc, constant-thickness sections and axial air inlet to establish a relation between vane camber and air turning angle for use in the design of this type of vane. Results regarding design rules for convergent annuli, example of the straight-line rule, design rule for constant axial velocity, and the comparison and use of design rules are provided.
Date: September 1950
Creator: Lieblein, Seymour
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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